CN217649623U

CN217649623U - Wing folding mechanism for unmanned aerial vehicle

Info

Publication number: CN217649623U
Application number: CN202221626744.0U
Authority: CN
Inventors: 贺军; 房佳琦; 梁国夏; 邓登宝
Original assignee: Zhuhai Tianqing Aerospace Technology Co ltd
Current assignee: Zhuhai Tianqing Aerospace Technology Co ltd
Priority date: 2022-06-27
Filing date: 2022-06-27
Publication date: 2022-10-25
Anticipated expiration: 2032-06-27

Abstract

The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to a wing folding mechanism for unmanned aerial vehicle, its wing includes fuselage mounting disc, self-lubricating copper sheathing, right wing mounting disc and left wing mounting disc surface pass through tight regulation screw and wing root metalwork fixed connection, and wing root metalwork fixed surface installs and is equipped with interior wing, the inside interior wing carbon pipe that is equipped with of interior wing, the inside fixed carbon tube spring that is equipped with of interior wing carbon pipe, the inside slip of interior wing carbon pipe is equipped with outer wing carbon pipe, the slip of interior wing surface is equipped with and cup joints and is equipped with the outer wing, and outside wing carbon pipe fixed connection is inside the outer wing, through in the same bomb tube, the wing adopts the box-like, upper and lower layering's overall arrangement scheme, can obtain double wing area, can improve the stability of aircraft and the speed of cruising. And compared with an electronic driving structure, the pure mechanical driving structure has higher reliability and simple realization principle.

Description

Wing folding mechanism for unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field specifically is a wing folding mechanism for unmanned aerial vehicle.

Background

Along with the progress of science and technology, the fixed wing catapult-assisted take-off unmanned aerial vehicle becomes the important operational strength in the aviation field in "unmanned aerial vehicle bee colony" tactics, and this unmanned aerial vehicle is common for folding the front and back wing in the shell cylinder, and after the transmission, unmanned aerial vehicle's front and back wing pop out, and the tail motive force starts immediately. In order to load more unmanned aerial vehicles, the unmanned aerial vehicles need to be as small as possible, but all the miniature unmanned aerial vehicles fly at low speed, have small wing loads and are easily influenced by unstable airflow, and the wings of the miniature unmanned aerial vehicles deviate from air routes in the process of high-wind and turbulent flow flight. The problem of small wingspan can be solved to wing retractable layout, but at present it is the electronic equipment drive wing extension that commonly used, and electronic equipment breaks down the frequency higher, once electronic equipment breaks down, the aircraft must appear the technical problem of taking off failure.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a wing folding mechanism for unmanned aerial vehicle to solve the problem that proposes in the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme:

the utility model provides a wing folding mechanism for unmanned aerial vehicle, wing folding mechanism include the wing, and wing folding mechanism still includes fuselage mounting disc, self-lubricating copper sheathing, right wing mounting disc and left wing mounting disc surface pass through tight regulation screw and wing root metalwork fixed connection, and wing root metalwork fixed surface installs and is equipped with the inner wing, the inside inner wing carbon pipe that is equipped with of inner wing, the inside fixed carbon pipe spring that is equipped with of inner wing carbon pipe, the inside slip of inner wing carbon pipe is equipped with outer wing carbon pipe, the slip of inner wing surface cup joints and is equipped with the outer wing, and outer wing carbon pipe fixed connection is inside the outer wing, the rotation of inner wing surface is equipped with outer wing latch hook, the inside fixed mounting of right wing mounting disc and left wing mounting disc is equipped with the torsional spring.

As the utility model discloses preferred scheme, be equipped with the protrusion extrusion portion in the middle of the outer wing latch hook, outer wing latch hook lower extreme is equipped with the latch hook baffle, and the fuselage mounting disc surface corresponds protrusion extrusion portion and is equipped with the leaf spring.

As the utility model discloses preferred scheme, the outer wing surface is equipped with the latch hook draw-in groove with outer wing latch hook looks adaptation.

As the preferred scheme of the utility model, the inner wing is connected with the inner part of the outer wing through the limiting rope.

As the utility model discloses preferred scheme, self-lubricating copper sheathing surface from the top down cup joints the installation in proper order and is equipped with down journal bearing, middle plane bearing and goes up journal bearing, and the right wing mounting disc is connected with last journal bearing fixed surface, and the left wing mounting disc is connected with journal bearing fixed surface down.

As the utility model discloses preferred scheme, it is equipped with the end cover through last plane bearing installation to go up the journal bearing upper end, and the journal bearing lower extreme is connected with the inside surface mounting under the fuselage mounting disc through lower plane bearing.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the utility model discloses in, through in the same shell drum, the wing adopts the overall arrangement scheme of box-like, upper and lower layering arrangement, can obtain double wing area, can improve the stability of aircraft and the speed of cruising. And compared with an electronic driving structure, the pure mechanical driving structure has higher reliability and simple realization principle.

Drawings

Fig. 1 is a perspective view of the rotating mechanism of the present invention;

fig. 2 is a cross-sectional view of the rotating mechanism of the present invention;

fig. 3 is a schematic structural view of an external mechanism of the wing of the present invention;

fig. 4 is a schematic structural view of a cross-sectional view of a wing of the present invention;

fig. 5 is a schematic structural view of the internal mechanism of the wing of the present invention;

fig. 6 is a schematic structural view of the outer wing latch hook mechanism of the present invention;

fig. 7 is a structural schematic diagram of the overall expanded state of the wing of the present invention;

fig. 8 is a structural schematic diagram of the overall storage state of the wing of the present invention.

In the figure: 1. a body mounting plate; 2. a right wing mounting plate; 3. a left wing mounting plate; 4, a lower plane bearing; 5. A lower radial bearing; 6. a middle plane bearing; 7. an upper radial bearing; 8. an upper flat bearing; 9. a torsion spring; 10. an end cap; 11. self-lubricating copper bush; 12. a plate spring; 13. an inner wing; 14. an outer wing; 15. a limiting rope; 16. an outer wing latch hook; 17. a latch hook baffle; 18. an inner fin carbon tube; 19. an outer fin carbon tube; 20. loosening and tightening the adjusting screw; 21. a wing root metal piece; 22. a carbon tube spring.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, rather than all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the scope of the present invention based on the embodiments of the present invention.

In order to facilitate understanding of the present invention, the present invention will be described more fully hereinafter with reference to the accompanying drawings. Several embodiments of the present invention are presented. The invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

Referring to fig. 1-8, the present invention provides a technical solution:

in the embodiment, referring to fig. 1, 2, 3, 4, 5, 6, 7, and 8, a wing folding mechanism for an unmanned aerial vehicle includes a wing, the wing folding mechanism further includes a fuselage mounting disc 1, a self-lubricating copper sleeve 11, a right wing mounting disc 2, and a left wing mounting disc 3, the surfaces of the right wing mounting disc 2 and the left wing mounting disc 3 are fixedly connected with a wing root metal part 21 through a slack adjusting screw 20, the surface of the wing root metal part 21 is fixedly mounted with an inner wing 13, an inner wing carbon tube 18 is arranged inside the inner wing 13, the inner wing carbon tube 18 is internally and fixedly provided with a carbon tube spring 22, the inner wing carbon tube 18 is internally and slidably provided with an outer wing carbon tube 19, when the aircraft ejects out of the barrel, because the inner wing 13 is not constrained by the torsion spring 9, the inner wing 13 is unfolded, when the inner wing 13 is unfolded, the inner wing 13 is pressed by the inner wing 13, the locking baffle 17 moves inwards, the outer wing 14 is unlocked, under the action of the spring 22, when 15 is tightened, the outer wing 14, the outer wing is stretched, the outer wing is connected to the outer wing 13, the outer wing is connected to the inner wing 13, the outer surface of the rotating limiting plate spring 13, the outer surface of the inner wing 13, the outer wing is provided with a left wing mounting disc 13, the torsion spring 12, and the outer wing is provided with a left wing mounting disc 13, and a left wing mounting disc 13 is provided with a left wing mounting disc 13, and a left wing mounting disc 13.

In an embodiment, referring to fig. 1, 2, 3, 4, 5, 6, 7 and 8, a convex pressing portion is disposed in the middle of the outer-wing latch hook 16, a latch hook stopper 17 is disposed at the lower end of the outer-wing latch hook 16, and a plate spring 12 is disposed on the surface of the body mounting plate 1 corresponding to the convex pressing portion.

In the embodiment, referring to fig. 1, 2, 3, 4, 5, 6, 7 and 8, a latch hook slot adapted to an outer wing latch hook 16 is formed in the surface of an outer wing 14, when an aircraft is in a barrel, the wings are in a contracted state, an inner wing 13 is pressed by a barrel wall to prevent a torsion spring 9 from rebounding, while the inner wing 13 is pressed, the inner wing 13 pushes a latch hook baffle 17 outwards, and a tightness adjusting screw 20 is installed at a contact position of the inner wing 13 and the latch hook baffle 17 to adjust the stroke of the latch hook baffle 17, so that the outer wing latch hook 16 can be ensured to clamp the outer wing 14, and the inner wing latch hook 16 can be prevented from being sprung to firmly clamp the outer wing 14.

In the embodiment, referring to fig. 1, 2, 3, 4, 5, 6, 7 and 8, the inner wing 13 and the outer wing 14 are connected by a limiting rope 15.

In the embodiment, referring to fig. 1, 2, 3, 4, 5, 6, 7 and 8, a lower radial bearing 5, a middle plane bearing 6 and an upper radial bearing 7 are sequentially installed on the surface of a self-lubricating copper sleeve 11 in a sleeved manner from top to bottom, a right wing installation disc 2 is fixedly connected with the surface of the upper radial bearing 7, a left wing installation disc 3 is fixedly connected with the surface of the lower radial bearing 5, a plate spring 12 is unlocked, an inner wing 13 is manually rotated backwards by about 80 degrees, an outer wing 14 is pushed from outside to inside, the inner wing 13 is rotated to be in a horizontal state with a fuselage after being pushed to the right position, the outer wing 14 needs to be pressed to be prevented from being ejected, and in the rotating process, the inner wing 13 pushes a latch hook baffle 17 to push an outer wing latch hook 16 outwards to lock the outer wing 14, and then the aircraft is loaded into a bomb tube to complete wing contraction.

In the embodiment, referring to fig. 1, 2, 3, 4, 5, 6, 7 and 8, an end cover 10 is installed at the upper end of an upper radial bearing 7 through an upper plane bearing 8, and the lower end of a lower radial bearing 5 is installed and connected with the inner lower surface of a fuselage mounting disc 1 through a lower plane bearing 4.

The working principle is as follows: when the aircraft is in a cartridge, the wings are in a contraction state, the inner wings 13 are pressed by the cartridge wall, the torsion spring 9 is prevented from rebounding, the inner wings 13 press the latch hook baffles 17 outwards (the contact parts of the inner wings 13 and the latch hook baffles 17 are provided with the tightness adjusting screws 20 to adjust the stroke of the latch hook baffles 17, so that the outer wing latch hooks 16 can clamp the outer wings 14) to prevent the inner wings from rebounding, the outer wing latch hooks 16 firmly clamp the outer wings 14, when the aircraft is ejected out of the cartridge, the inner wings 13 are unfolded due to the fact that the inner wings 13 are not constrained by the cartridge wall, the torsion spring 9 rebounds, the inner wings 13 are unfolded, when the inner wings 13 are unfolded, the latch hook baffles 17 are pressed to generate the inner springs because the latch hook baffles 17 lose the compression of the inner wings 13, the latch hook baffles 17 move inwards to unlock the outer wings 14, the outer wings 14 are popped and unfolded under the action of the carbon tube springs 22, when the inner wings 15 are tightened, the inner wings 13 are locked by the leaf springs 12 respectively, and the aircraft enters a cruising state;

the plate spring 12 is unlocked, the inner wing 13 is manually rotated backwards by about 80 degrees, the outer wing 14 is pushed from outside to inside, the inner wing 13 is rotated to be horizontal to the airplane body after being pushed in place, the outer wing 14 needs to be compressed to prevent ejection in the process, the inner wing 13 can push the lock hook baffle 17 to push the outer wing lock hook 16 outwards in the rotating process, the outer wing 14 is locked, the airplane is loaded into the bomb tube to complete wing contraction, and therefore the wings of the unmanned aerial vehicle are driven to be folded and unfolded by adopting a pure mechanical structure without being driven by electronic equipment.

Particularly, wings of the unmanned aerial vehicle adopt a nested and vertically layered layout scheme, double wing areas can be obtained in the volume of a conventional wing, the space utilization rate is high, the lift-drag ratio is large, a traditional electronic equipment driving mechanism is abandoned, a pure mechanical rotating mechanism is used for driving the wings to be folded and unfolded, the production cost is reduced, the phenomenon that the wings cannot be folded and unfolded normally when the electronic equipment breaks down is prevented, and the reliability is improved.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a wing folding mechanism for unmanned aerial vehicle, wing folding mechanism includes the wing, wing folding mechanism still includes fuselage mounting disc (1), self-lubricating copper sheathing (11), right wing mounting disc (2) and left wing mounting disc (3), its characterized in that: right side wing mounting disc (2) and left wing mounting disc (3) surface are through tight regulation screw (20) and wing root metalwork (21) fixed connection, and wing root metalwork (21) fixed surface installs and is equipped with interior wing (13), interior wing (13) inside is equipped with interior wing carbon pipe (18), interior wing carbon pipe (18) inside fixed is equipped with carbon pipe spring (22), interior wing carbon pipe (18) inside slip is equipped with outer wing carbon pipe (19), interior wing (13) surface slip cup joints and is equipped with outer wing (14), and outer wing carbon pipe (19) fixed connection is inside outer wing (14), interior wing (13) surface rotation is equipped with outer wing latch hook (16), right side wing mounting disc (2) and left wing mounting disc (3) inside fixed mounting are equipped with torsional spring (9).

2. A wing fold mechanism for a drone according to claim 1, characterized in that: the middle of the outer wing lock hook (16) is provided with a convex extrusion part, the lower end of the outer wing lock hook (16) is provided with a lock hook baffle (17), and the surface of the machine body mounting disc (1) is provided with a plate spring (12) corresponding to the convex extrusion part.

3. A wing fold mechanism for a drone according to claim 1, characterized in that: the surface of the outer wing (14) is provided with a lock hook clamping groove matched with the outer wing lock hook (16).

4. A wing fold mechanism for a drone according to claim 1, characterized in that: the inner wing (13) is connected with the inner part of the outer wing (14) through a limiting rope (15).

5. A wing fold mechanism for a drone according to claim 1, characterized in that: self-lubricating copper sheathing (11) surface from the top down cup joints the installation in proper order and is equipped with down journal bearing (5), middle plane bearing (6) and last journal bearing (7), and right wing mounting disc (2) and last journal bearing (7) fixed surface are connected, and left wing mounting disc (3) and journal bearing (5) fixed surface are connected down.

6. A wing folding mechanism for unmanned aerial vehicles according to claim 5, characterized in that: the upper end of the upper radial bearing (7) is provided with an end cover (10) through an upper plane bearing (8), and the lower end of the lower radial bearing (5) is connected with the inner lower surface of the machine body installation disc (1) through a lower plane bearing (4).